JPH03204597A - Guided missile launching device - Google Patents
Guided missile launching deviceInfo
- Publication number
- JPH03204597A JPH03204597A JP34289689A JP34289689A JPH03204597A JP H03204597 A JPH03204597 A JP H03204597A JP 34289689 A JP34289689 A JP 34289689A JP 34289689 A JP34289689 A JP 34289689A JP H03204597 A JPH03204597 A JP H03204597A
- Authority
- JP
- Japan
- Prior art keywords
- guided missile
- cooling
- pressure gas
- launching
- sensor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001816 cooling Methods 0.000 claims abstract description 22
- 239000007789 gas Substances 0.000 abstract description 22
- 239000000112 cooling gas Substances 0.000 abstract description 10
- 238000002347 injection Methods 0.000 abstract 1
- 239000007924 injection Substances 0.000 abstract 1
- 238000010304 firing Methods 0.000 description 4
- 239000003721 gunpowder Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 239000003507 refrigerant Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は誘導弾発射装置に関し、特に可搬形の小形軽量
な誘導弾用の誘導弾発射装置に間する。DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a guided missile launcher, and more particularly to a portable, small and lightweight guided missile launcher for guided missiles.
従来の誘導弾発射装置は、誘導弾を発射させるためのブ
ースタとして専用のガス、または火薬を用いていた。Conventional guided missile launchers have used dedicated gas or gunpowder as a booster for launching guided missiles.
第2図は従来の誘導弾発射装置の断面斜視図である。第
2図の誘導弾発射装置は、オペレータが肩に搭載し空中
の目標に向って誘導する小形軽量な誘導弾用の発射装置
であり、発射筒6に誘導弾10を装備し、握手11及び
引金12で発射用火薬8に点火し誘導弾10を発射させ
る。FIG. 2 is a cross-sectional perspective view of a conventional guided missile launcher. The guided missile launcher shown in FIG. 2 is a small and lightweight guided missile launcher that is carried on the shoulder of an operator and guided toward a target in the air. The gunpowder 8 is ignited by a trigger 12, and a guided bullet 10 is fired.
この場合、センサ部14は誘導体10の頭部に配設され
、通常的70°K(ケルビン温度)程度に冷却して利用
される赤外線検知器などのセンサが多用されている。こ
の冷却用としての冷媒を封入する高圧ガス封入の冷却ガ
スボンベ9は、その噴出ガスによってセンサ部14のセ
ンサを冷却している。In this case, the sensor unit 14 is disposed at the head of the inductor 10, and a sensor such as an infrared detector that is cooled to about 70°K (Kelvin temperature) is commonly used. The cooling gas cylinder 9 filled with high-pressure gas and containing a refrigerant for cooling cools the sensor of the sensor section 14 with its ejected gas.
上述した従来の誘導弾発射装置では、誘導弾を発射させ
るために、専用の発射装置を必要とするため、寸法1重
量か大きくなり、部品点数も多くなるという欠点がある
。The above-described conventional guided missile launcher requires a dedicated launcher in order to launch the guided missile, which has the drawbacks of an increase in size and weight and an increase in the number of parts.
本発明の誘導弾発射装置は、センサ冷却用高圧カスと誘
導弾発射時にブースタとして用いる構成を有する。The guided missile launcher of the present invention has a high-pressure gas for cooling the sensor and a configuration used as a booster when launching the guided missile.
次に、図面を参照して本発明を説明する。 Next, the present invention will be explained with reference to the drawings.
第1図は本発明の一実施例の部分断面斜視図であり、冷
却/発射用高圧カスボンベ1と、ガス噴出口2と、頭部
にセンサを含むセンサ冷却部7を配設した誘導弾5が発
射筒6に配備された状態を示し、冷却/発射用高圧ガス
ボンベ1とセンサ冷却部7とは冷却ガス配管4で結合し
、かつ冷却ガス配管4の冷却/発射用高圧ガスボンベ1
測には逆流防止弁3が設けられた構造となっており、さ
らに発射筒6の外側には照準用スコープ13が配設され
ている。FIG. 1 is a partial cross-sectional perspective view of an embodiment of the present invention, in which a high-pressure gas cylinder 1 for cooling/launching, a gas outlet 2, and a guided missile 5 having a sensor cooling section 7 including a sensor in its head are disposed. is installed in the launch tube 6, the high-pressure gas cylinder 1 for cooling/firing and the sensor cooling unit 7 are connected by a cooling gas pipe 4, and the high-pressure gas cylinder 1 for cooling/firing of the cooling gas pipe 4 is connected to the sensor cooling unit 7.
The system is equipped with a check valve 3, and an aiming scope 13 is provided outside the launch tube 6.
次に、第1図の実施例の動作について説明する。Next, the operation of the embodiment shown in FIG. 1 will be explained.
冷却/発射用高圧ガスボンベ1は、センサ冷却部7と冷
却カス配管4で接続されており、誘導弾5が発射される
まで高圧ガスを供給してセンサに噴出、冷却する。誘導
弾5の発射時には、噴出口2が開き、高圧ガスの噴出の
反作用により誘導弾5が発射筒6から発射される。誘導
弾5の推進装置が点火すると同時に、高圧ガスボンベは
誘導弾から切り離され、逆流防止弁3が閉じて、残流カ
スの逆流を防ぐ構造となっている。誘導弾は初期冷却状
態で機能を確保しつつ、たがだが数秒程度飛翔して運用
目的を完了する。The cooling/launching high-pressure gas cylinder 1 is connected to the sensor cooling unit 7 through a cooling waste pipe 4, and supplies high-pressure gas to the sensor until the guided projectile 5 is fired, thereby cooling the sensor. When the guided bullet 5 is fired, the ejection port 2 is opened, and the guided bullet 5 is fired from the launch tube 6 due to the reaction of the jet of high-pressure gas. At the same time as the propulsion device for the guided missile 5 is ignited, the high-pressure gas cylinder is separated from the guided missile, and the check valve 3 is closed to prevent the residual scum from flowing back. Guided missiles maintain their functionality in their initial cooling state, and fly for a few seconds to complete their operational purpose.
以上説明したように本発明は、冷却用高圧ガスを誘導弾
発射のためのブースタとして利用することにより、誘導
弾内部に冷却用ガスボンベを搭載する必要が無くなり、
誘導弾の著しい小型化、軽量化ができるという効果があ
る。As explained above, the present invention uses high-pressure cooling gas as a booster for launching guided missiles, thereby eliminating the need to mount a cooling gas cylinder inside the guided missile.
This has the effect of significantly reducing the size and weight of guided missiles.
第1図は本発明の誘導弾発射装置の部分断面斜視図、第
2図は従来の誘導弾発射装置の部分断面斜視図である。
1・・・冷却/発射用高圧ガスボンベ、2・・・ガス噴
出口、3・・・逆流防止弁、4・・・冷却ガス配管、5
・・誘導弾、6・・・発射筒、7・・・センサ冷却部、
8・・・発射用火薬、9・・・冷却カスボンベ、10・
・・誘導弾、11・・・握手、12・・・引金、13・
・・照準用スコープ。FIG. 1 is a partially sectional perspective view of a guided missile launcher according to the present invention, and FIG. 2 is a partially sectional perspective view of a conventional guided missile launcher. 1... High-pressure gas cylinder for cooling/firing, 2... Gas outlet, 3... Backflow prevention valve, 4... Cooling gas piping, 5
...Guided missile, 6. Launcher, 7. Sensor cooling unit,
8... Gunpowder for firing, 9... Cooling gas cylinder, 10.
...Guided bullet, 11...Handshake, 12...Trigger, 13.
・Aiming scope.
Claims (1)
用いることを特徴とする誘導弾発射装置。A guided missile launcher characterized in that high pressure gas for sensor cooling is used as a booster when launching guided missiles.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP34289689A JPH03204597A (en) | 1989-12-29 | 1989-12-29 | Guided missile launching device |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP34289689A JPH03204597A (en) | 1989-12-29 | 1989-12-29 | Guided missile launching device |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH03204597A true JPH03204597A (en) | 1991-09-06 |
Family
ID=18357355
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP34289689A Pending JPH03204597A (en) | 1989-12-29 | 1989-12-29 | Guided missile launching device |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH03204597A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108827072A (en) * | 2018-08-24 | 2018-11-16 | 杜蘅轩 | It is a kind of can inflation/deflation transmitting moving system |
-
1989
- 1989-12-29 JP JP34289689A patent/JPH03204597A/en active Pending
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108827072A (en) * | 2018-08-24 | 2018-11-16 | 杜蘅轩 | It is a kind of can inflation/deflation transmitting moving system |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US5952601A (en) | Recoilless and gas-free projectile propulsion | |
US20080223977A1 (en) | Methods and apparatus for projectile guidance | |
JPS628720B2 (en) | ||
US4137893A (en) | Riot control weapon | |
US11740039B2 (en) | Apparatus and method for accelerating an object via an external free jet | |
US6530305B1 (en) | Telescoping pressure-balanced gas generator launchers for underwater use | |
US3167016A (en) | Rocket propelled missile | |
US6012375A (en) | Aircraft infrared guided defense missile system | |
US5202530A (en) | Light armor piercing automatic rifle | |
EP0549659A1 (en) | A device for firing a projectile. | |
US3903802A (en) | Shell construction sealing washer | |
US3326128A (en) | Rockets and combinations of rockets and cases | |
US2681619A (en) | Rocket projectile | |
US5099764A (en) | Propulsion unit fireable from an enclosure | |
US2397800A (en) | Gun | |
US4038903A (en) | Two stage telescoped launcher | |
JPH03204597A (en) | Guided missile launching device | |
US4601278A (en) | Ammunition cartridge | |
US6000340A (en) | Rocket launching system employing thermal-acoustic detection for rocket ignition | |
US20050188976A1 (en) | Large Gauge Pneumatic Launcher | |
US4644843A (en) | Gas actuated gun system for launching a projectile | |
US3583277A (en) | Closed breech launch tube and valve means therefore | |
RU2631958C1 (en) | Reactive engine, method for shooting with rocket ammunition and rocket ammunition | |
WO1989004451A1 (en) | Recoil-less launch system | |
US3380382A (en) | Gun launched liquid rocket |